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NACA 23112 (naca23112-jf)

NACA 23112 - NACA 23112 5 digit reflex airfoil


Airfoil naca23112-jf
Details Dat file Parser  
(naca23112-jf) NACA 23112
NACA 23112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord.
Max camber 1.2% at 14.7% chord
Source Javafoil generated
Source dat file
The dat file is in Selig format
NACA 23112
1.00000642	0.00125998
0.99932175	0.00135960
0.99726965	0.00165788
0.99385593	0.00215318
0.98909020	0.00284276
0.98298587	0.00372289
0.97556012	0.00478884
0.96683380	0.00603501
0.95683136	0.00745499
0.94558080	0.00904163
0.93311351	0.01078717
0.91946425	0.01268323
0.90467094	0.01472097
0.88877462	0.01689109
0.87181927	0.01918386
0.85385169	0.02158917
0.83492138	0.02409648
0.81508035	0.02669485
0.79438303	0.02937287
0.77288606	0.03211860
0.75064817	0.03491954
0.72772999	0.03776252
0.70419392	0.04063368
0.68010393	0.04351837
0.65552541	0.04640112
0.63052499	0.04926560
0.60517038	0.05209467
0.57953019	0.05487032
0.55367376	0.05757383
0.52767097	0.06018580
0.50159210	0.06268632
0.47550763	0.06505515
0.44948808	0.06727191
0.42360383	0.06931635
0.39792499	0.07116863
0.37252114	0.07280956
0.34746125	0.07422094
0.32281345	0.07538588
0.29864488	0.07628902
0.27502151	0.07691691
0.25200795	0.07725814
0.22966728	0.07730364
0.20802116	0.07704596
0.18684616	0.07642403
0.16620800	0.07531014
0.14624617	0.07360310
0.12710239	0.07123831
0.10891713	0.06818911
0.09182539	0.06446620
0.07595223	0.06011508
0.06140856	0.05521140
0.04828757	0.04985472
0.03666245	0.04416103
0.02658555	0.03825477
0.01808884	0.03226111
0.01118545	0.02629871
0.00587191	0.02047377
0.00213064	0.01487514
-0.00006773	0.00957077
-0.00076226	0.00460553
0.00000000	0.00000000
0.00213272	-0.00415084
0.00554583	-0.00777231
0.01018102	-0.01090383
0.01598049	-0.01359774
0.02288873	-0.01591613
0.03085464	-0.01792743
0.03983402	-0.01970285
0.04979209	-0.02131304
0.06070591	-0.02282508
0.07256603	-0.02429996
0.08537720	-0.02579049
0.09915762	-0.02733933
0.11393691	-0.02897692
0.12975278	-0.03071885
0.14664705	-0.03256260
0.16466139	-0.03448344
0.18383345	-0.03642987
0.20419359	-0.03831882
0.22569368	-0.04003354
0.24799205	-0.04149882
0.27098799	-0.04271137
0.29461848	-0.04367333
0.31881860	-0.04438874
0.34352176	-0.04486335
0.36865982	-0.04510443
0.39416332	-0.04512066
0.41996170	-0.04492182
0.44598346	-0.04451870
0.47215642	-0.04392282
0.49840790	-0.04314629
0.52466499	-0.04220163
0.55085471	-0.04110164
0.57690427	-0.03985927
0.60274131	-0.03848757
0.62829406	-0.03699960
0.65349159	-0.03540842
0.67826402	-0.03372710
0.70254272	-0.03196870
0.72626051	-0.03014636
0.74935183	-0.02827329
0.77175297	-0.02636283
0.79340222	-0.02442852
0.81424004	-0.02248409
0.83420923	-0.02054351
0.85325509	-0.01862095
0.87132556	-0.01673079
0.88837134	-0.01488754
0.90434605	-0.01310577
0.91920632	-0.01139999
0.93291189	-0.00978450
0.94542573	-0.00827328
0.95671410	-0.00687978
0.96674663	-0.00561671
0.97549639	-0.00449590
0.98293995	-0.00352807
0.98905740	-0.00272266
0.99383241	-0.00208765
0.99725224	-0.00162941
0.99930779	-0.00135258
0.99999358	-0.00125998

Dat file parser warnings
  • Line 2 - X value too large but included: 1.00000642 0.00125998
  • Line 60 - X value too small but included: -0.00006773 0.00957077
  • Line 61 - X value too small but included: -0.00076226 0.00460553
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Polars for NACA 23112 (naca23112-jf)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca23112-jf50,000922.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23112-jf50,000527.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23112-jf100,000934.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23112-jf100,000539.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23112-jf200,000950.6 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23112-jf200,000555.5 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23112-jf500,000977.9 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23112-jf500,000578.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23112-jf1,000,000998.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23112-jf1,000,000595.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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